陆基巡航导弹四组合制导系统仿真研究

对陆基巡航导弹四组合制导技术,以一条典型轨迹进行了全航线仿真研究,包括初始对准段以及INS/GPS组合段、INS/TERCOM（地形轮廓匹配）组合段、INS/GPS/TERCOM组合段和INS/SMNS（景像匹配导航系统）组合段等共24个航段的研究。仿真结果表明:静基座初始对准能达到对准时间<4min,水平对准精度<21”,方位对准精度<2’;INS/GPS组合的位置精度达到30m（CEP）,速度精度<0.2 m/s（CEP）;INS/GPS/TERCOM组合可达到INS/GPS与TERCOM（为半个网格的精度）中的较高者;INS/SMNS可达到0.5像素（10 m/pixel的分辨率）的位置精度和0.2 m/s的速度精度。在SMN对INS修正后,经15s纯INS飞行后的命中精度为6～10m（CEP）。

Simulation on INS/GPS/TERCOM/SMNS Integrated Guidance System for Continent-Based Cruise Missile

INS (Inertial Navigation System) /GPS/TERCOM (Terrain Contour Matching) /SMNS (Scene Matching Navigation System) integrated guidance technology for continent-based cruise missile is discussed in this paper. Simulation is made on a typical track, including the initial alignment segment, INS/GPS segment, INS/TERCOM segment, INS/GPS/TERCOM segment and INS/SMNS segment. Simulation results show that static-base initial alignment can reach the accuracy of alignment time<4' , level angle error<21" and azimuth angle error < 2' ; INS/GPS can reach the position level of 30 m (CEP) and velocity level 0.2 m/s; INS/GPS/TERCOM can reach the higher accuracy of INS/GPS and TERCOM (half of the grid size); INS/SMNS can achieve the accuracy of position <0.5 pixel (resolution of 10 m/pixel) and velocity <0.2 m/s. The hit level of 6-10 m (CEP) is achieved with pure-INS flight after INS being corrected by SMNS. The accuracy of integrated navigation/guidance algorithms discussed in this paper can meet the requirement of cruise missile guidance.